Ram air turbine

ABSTRACT

A ram air turbine comprises a turbine housing which mounts a number of circumferentially spaced turbine blades that function predominantly as impulse turbine blades and a number of splitters, each located in between adjacent turbine blades, which function predominantly as a reaction turbine blade but are shorter in length than the turbine blades. The cross section of the turbine housing decreases between its forward and aft ends while the height of both the turbine blades and splitters increases in the same direction such that the tips of the turbine blades and splitters collectively form a substantially cylindrical shape.

FEDERALLY SPONSORED RESEARCH

This invention was made with government support under Small BusinessInnovation Research Contract Nos. N68335-08-C-0276 and N68335-09-C-0313awarded by the United States Navy. The government has certain rights inthe invention.

FIELD OF THE INVENTION

This invention relates to a ram air turbine particularly adapted for usewith a submerged ram air turbine generating system whose operation isbased on free stream flow in which power generation is derived from thekinetic energy of a stream of fluid and the system is designed tomaximize the velocity and mass flow of the fluid from a submerged inletthrough adjustable exhaust panels.

BACKGROUND OF THE INVENTION

Ram air turbines are commonly used in military and commercial aircraftto provide a source of hydraulic or electrical power in the event of anemergency. Modern aircraft generate power through the main engines orvia an auxiliary power unit such as a fuel-burning turbine typicallylocated in the tail of the aircraft. In most applications for commercialaircraft, ram air turbines are retracted into the fuselage or wing(s)under normal operating conditions, but are deployed in the event of anemergency loss of power. They typically comprise two or more blades,much like windmill blades, carried by a shaft which is coupled to agenerator. The blades rotate the shaft in response to contact with theair stream produced by movement of the aircraft during flight. Dependingupon the size of the blades, the capacity of the electrical generatorand the flight speed of the aircraft, ram air turbines can supply asmuch as 70 kW for use in powering flight controls, linked hydraulics andflight-critical instrumentation.

Military aircraft, particularly those designed for electronic warfare,have in the past typically used ram air turbines externally mounted to apod to deliver power for electronic equipment employed to counter enemyair defenses using reactive and/or pre-emptive jamming techniques, toprovide stand-off escort jamming, to initiate electronic attacks and toprovide self-protection capability for the aircraft. A pod isessentially a generally cylindrical, aerodynamically-shaped housingmounted to the underside of the aircraft wings. More recently, submergedram air turbines have been proposed as a replacement for externallymounted designs. The term “submerged” in this context refers to theplacement of ram air turbines within the interior of pods in alignmentwith one or more inlets which direct a flow of air onto the blades ofthe turbine which is then exhausted through the pod outlet(s).

The increasing sophistication of electronic equipment employed inmilitary aircraft has created a requirement for additional power atflight speeds of 200 to 220 knots. Existing externally mounted andsubmerged ram air turbines do not provide sufficient power output, andthere is a need for an improved ram air turbine generating system.

SUMMARY OF THE INVENTION

This invention is directed to a ram air turbine that may be use with asubmerged ram air turbine generating system, which, in one presentlypreferred application, is capable of generating in excess of 100 kW ofpower when mounted to the pod of an aircraft flying at speeds of about220 knots and at an altitude of about 25,000 feet.

In one presently preferred embodiment, the ram air turbine comprises aturbine housing having a forward end, an aft end, and an outer surfacecollectively defining a hollow interior. The turbine housing decreasesin cross section from its forward to aft end. A number of turbineblades, which function predominantly as impulse turbine blades, arecircumferentially spaced around the outer surface of the turbinehousing. A like number of splitters, each located in between adjacentturbine blades, function predominantly as an impulse turbine blade. Eachof the turbine blades and the splitters have a forward end located atthe forward end of the turbine housing, but while the turbine bladesextend to the aft end of the turbine housing the splitters are onlyabout one-half of the length of the turbine blades thus forming openareas near the aft end of the turbine housing between adjacent turbineblades. Each turbine blade has a blade tip and each splitter has asplitter tip, with the blade tips and splitter tips collectively form agenerally cylindrical shape. The height of both the turbine blades andsplitters increases from the forward end of the turbine housing towardits aft end.

BRIEF DESCRIPTION OF THE DRAWINGS

The structure, operation and advantages of the presently preferredembodiment of this invention will become further apparent uponconsideration of the following description, taken in conjunction withthe accompanying drawings, wherein:

FIG. 1 is a perspective view of the submerged ram air turbine generatingsystem of this invention in the particular application wherein it isutilized with a pod for mounting to the wing or other location on anaircraft;

FIG. 2 is a cross sectional view of a portion of the pod shown in FIG.1;

FIG. 3 is a plan view of one set of louvers located in the submergedinlet of the system, depicted in the closed position;

FIG. 4 is a cross sectional, side elevational view of the louvers shownin FIG. 3 in the closed position;

FIG. 5 is a view similar to FIG. 4 except with the louvers in an openposition;

FIG. 6 is an end view of the inlet guide vanes as viewed from theupstream end of the hybrid ram air turbine;

FIG. 7 is an end view of an alternative embodiment of the inlet guidevanes wherein the angle of such vanes is adjustable;

FIG. 8 is a cross sectional view taken generally along line 11-11 ofFIG. 10;

FIG. 9 is a side elevational view of the adjustable inlet guide vanesdepicted in FIGS. 10 and 11;

FIG. 10 is an enlarged view of the encircled portion of FIG. 12illustrating the change in angle of the inlet guide vanes in response toactuation of a control arm;

FIG. 11 is a perspective view of the hybrid ram air turbine of thisinvention;

FIG. 12 is an end view of the hybrid ram air turbine shown in FIG. 14;

FIG. 13 is a schematic representation of inlet guide vanes, a turbineblade and a splitter showing the deflection of an air stream by thevanes onto the blade and splitter;

FIG. 14 is a perspective view of the hybrid ram air turbine of thisinvention in which a single turbine blade is shown;

FIG. 15 is a side elevational view of FIG. 14;

FIG. 16 is a plan view of FIG. 14;

FIG. 17 is an end view of FIG. 14, as seen from the aft end of thehybrid ram air turbine;

FIG. 18 is an end view of FIG. 14, as seen from the forward end of thehybrid ram air turbine; and

FIG. 19 is a partial view of the aft portion of the submerged ram airturbine generating system of this invention depicting one of the exhaustpanels and its connection to a drive motor via a gear reducer andactuator ring.

DETAILED DESCRIPTION OF THE INVENTION

Referring initially to FIGS. 1 and 2, the submerged ram air turbinegenerating system 10 of this invention is depicted in one preferredapplication wherein it is incorporated into a pod 12 typically mountedto the underside of the wing of an aircraft (not shown). The pod 12generally includes a pod housing 14 having an outer surface 15, aforward end 16, an aft end 18 and a hollow interior 20. For purposes ofthe present discussion, the terms “forward,” “aft,” “upstream” and“downstream” refer to the direction of a flow of air depicted by arrows22 and 24 in FIG. 2. In particular, air flowing over the pod 12 duringflight of an aircraft impacts the forward end 16 of the pod housing 16first, and a portion of such flow identifies as air stream 22 enters thepod interior 20 through a submerged inlet 26 of the system 10, discussedbelow, while the remaining portion of the flow denoted as air stream 24continues along the outer surface 15 of the pod housing 16.Additionally, the terms “inner,” “outer,” and “radially” denote spatialorientations relative to the outer surface 15 of the pod housing 14 andits hollow interior 20, i.e. the interior 20 of the pod housing 14 islocated radially inwardly from its outer surface 15. It should beunderstood that term “radially” when used to describe positions ofelements in relation to the pod 14 is not intended to be limited to adirection from the center of a circular or cylindrical shape but isapplicable to essentially any shape such as oval, rectangular etc.

In addition to the submerged inlet 26, the system 10 may include aclosure device in the form of adjustable louvers 28 located in thesubmerged inlet 26, a stator comprising inlet guide vanes 30 which maybe adjustable, a hybrid ram air turbine 32 directly coupled to apermanent magnet generator 34, and, adjustable exhaust panels 36. Eachof these components of system 10 is discussed separately below.

Considering initially the submerged inlet 26, reference is made to FIGS.1 and 2. In the presently preferred embodiment, the submerged inlet 26is located downstream from the forward end 16 of the pod 12 and not atthe nose or forward end 16 as contemplated, for example, in systems ofthe type disclosed in U.S. Pat. No. 6,270,309. The submerged inlet 26preferably extends around substantially the entire periphery of theouter surface 15 of the pod housing 14, e.g. up to 360° in theconfiguration of pod 12 illustrated in the drawings. It includes acurved inlet opening 38 located at the outer surface 15 of the podhousing 14 which is effective to resist flow separation of the airstream 22 as it enters the pod interior 20. Preferably, the crosssectional area of the submerged inlet 26 converges or decreases from thecurved inlet opening 38 to the area of the inlet guide vanes 30 where itterminates. Accordingly, the term “submerged inlet” as used herein meansa passageway extending into the interior of the pod housing 14,preferably but not necessarily converging in cross section, having anentrance defined by the curved inlet opening 38 which is substantiallyflush with outer surface 15 of the pod housing 14 at a point of maximumdiameter of the pod housing 14. As such, the submerged inlet 26 is notvisible when viewing the pod housing 14 from the forward end or aft end,and it is not exposed to ram air. This construction is in contrast tomany conventional ram air turbine systems in which one or more inletsproject outwardly from the outer surface of the housing or otherstructure within which the ram air turbine is enclosed, or wherein theinlet is located at the nose of the housing.

Referring now to FIGS. 3-5, a closure device in the form of a number ofsets 40 of louvers 42 is mounted in the submerged inlet 26. One set 40of louvers 42 is shown in the Figs., it being understood that a numberof other groups or sets 40 of louvers 42 are circumferentially spacedalong the entire extent of the submerged inlet 26. As schematicallydepicted in the drawings, the individual louvers 42 within each set 40are oriented side-by-side and connected at one edge to a control rod 44.The control rod 44 is movable in the direction of arrow 46 shown in FIG.3 to cause the louvers 42 to move between a closed position depicted inFIG. 4 and an open position shown in FIG. 5. A separate control rod 44is employed for each set 40 of louvers 42, and the control rods 44 maybe collectively actuated by a motor and drive mechanism (not shown) orother suitable means.

The inlet guide vanes 30 are illustrated in more detail in alternativeembodiments shown in FIG. 6, and in FIGS. 7-10. In both of theseembodiments, the inlet guide vanes 30 act as a stator to direct the airstream 22 onto the ram air turbine 32. In FIG. 6 the guide vanes 30 arefixed, whereas in FIGS. 7-10 their angle may be adjusted, as describedbelow.

Referring initially to FIG. 6, a number of inlet guide vanes 30 arecircumferentially arranged between an inner ring 48 and an outer ring50. As best seen in FIG. 2, the inner ring 48 is connected to a bracket52 secured to the pod housing 14 and the outer ring 50 is directlyconnected to the pod housing 14. Each of the vanes 30 has an inner edge54 affixed to the inner ring 48, an outer edge 56 mounted to the outerring 50, a leading end 58 and a trailing end 60. See also FIG. 13. Inthe presently preferred embodiment, each of the vanes 30 decreases inheight, i.e. the dimension between the inner and outer edges 54, 56thereof, in a direction from the leading end 58 to the trailing end 60.The vanes 30 each have a dished or cup-shaped surface 62 extendingbetween their leading and trailing ends 58, 60, and they are oriented atan angle with respect to the air stream 22 as described more fully belowin connection with a discussion of the operation of the system 10 andFIG. 13.

In the alternative embodiment illustrated in FIGS. 7-10, the inlet guidevanes 30 may be adjusted in such as way as to vary the angle at whichtheir dished surfaces 62 are oriented relative to the air stream 22 andthe hybrid ram air turbine 32. See also FIG. 13 and the discussionbelow. Each of the vanes 30 has the same configuration as that depictedin FIG. 6, with inner edge 54 mounted by a shaft 64 to inner ring 48 andouter edge 56 mounted on a shaft 66 to outer ring 50. A control arm 68extends along the outer ring 50 and is connected to each of the shafts66. The control arm 68 is movable in a circumferential direction asindicated by the arrow 69 in FIG. 10 causing the vanes 30 to pivot onshafts 64, 66 in the direction of arrow 70 to an extent illustrated bythe two positions of vanes 30 depicted in phantom lines in FIG. 10. Thecontrol arm 68 may be moved by a mechanical connection to a motor (notshown) or other suitable means.

Referring now to FIGS. 2 and 11-18, the hybrid ram air turbine 32 ofthis invention is illustrated. The turbine 32 comprises a turbinehousing 72 having a forward end 74, an aft end 76, an outer surface 78and a hollow interior 80. The cross section of the turbine housing 72decreases in a direction from the forward end 74 to the aft end 76forming an essentially frusto-conical shape. As best seen in FIG. 2, aturbine shaft 82 is centrally mounted within the housing interior 80 ona rear bearing 84 at one end and a forward bearing 86 at the oppositeend. The rear bearing 84 is carried on a support plate 88 connected tothe pod housing 14, and is held in place on the turbine shaft 82 by alocking ring 90. The forward bearing 86 is mounted to a forward bearingsupport 92, which, in turn, is connected to the inner ring 48 whichsupports the inlet guide vanes 30. The forward bearing 86 is also heldin place on the turbine shaft 82 by a locking ring 90. The turbinehousing 72 is connected to the turbine shaft 82, so that they rotate inunison, by an aft turbine bracket 94 and a forward turbine bracket 96.

In the presently preferred embodiment, the turbine shaft 82 is directlyconnected by a flex coupling 98 to the input shaft 100 of generator 34.No gear box, lubrication system or other interface connection betweenturbine shaft 82 and generator 34 is required. The generator 34 issupported in position relative to the turbine shaft 82 by the inner ring48. As noted above, the generator 34 is preferably a permanent magnetgenerator, although it is contemplated that other types of generatorsmay be employed. Additionally, as schematically depicted in FIG. 2,power control electronics 102 may be coupled to or integrated with thegenerator 34 to supply a constant voltage output to electronic devices(not shown) typically located in the forward end 16 of the pod 12. Thepower control electronics 102 are effective to either boost or buck thevoltage output of the generator 34 independently of the torque and/orshaft speed of the turbine 32. Details of the generator 34 and powercontrol electronics 102 form no part of this invention and are thereforenot discussed herein.

The hybrid ram air turbine 32 of this invention is formed with a numberof turbine blades 104 which are circumferentially spaced about theturbine housing 72, and a number of splitters 106 each located inbetween adjacent blades 104. Each of the blades 104 comprises a bladeroot 108 connected to or integrally formed with the turbine housing 72,a blade tip 110 radially outwardly spaced from the blade root 108, aforward end 112 and an aft end 114. The blades 104 extend the entirelength of the turbine housing 72, e.g. from its forward end 74 to theaft end 76. Each of the splitters 106 comprises a splitter root 116connected to or integrally formed with the turbine housing 72, asplitter tip 118 radially outwardly spaced from the splitter root 116, aforward end 120 and an aft end 122. Each splitter 106 extends from theforward end 74 of the turbine housing 72 to a terminal location spacedfrom its aft end 76, preferably about 50% to 60% of the total length ofthe blades 104, thus forming an open area 124 between adjacent blades104 where each splitter 106 terminates. See FIG. 11.

In the presently preferred embodiment, the blade tips 110 of the blades104 and the splitter tips 118 of the splitters 106 collectively form agenerally cylindrical shape from the forward end 74 of the turbinehousing 72 to its aft end 76. Consequently, the height dimension of theblades 104, as measured between the blade roots 108 and blade tips 110,and the height dimension of the splitters 106, as measured between thesplitter roots 116 and splitter tips 118, increases from the forward end74 of the turbine housing 72 to its aft end 76 by the same amount as thecross sectional area of the turbine housing 72 decreases in thatdirection. Compared to prior art turbines, the hybrid ram air turbine 32of this invention has a high cord to diameter ratio. The term “cord” asused herein refers to the length of the blade root 108 of blades 104along the turbine housing 72, and “diameter” refers to the diameter ofthe turbine housing 72. A specific example of this dimensionalrelationship is given below with reference to a discussion of FIGS.14-18.

The geometry of the turbine blades 104 is generally similar to that ofblades used in a radial turbine in which fluid flow is directed radiallyonto the blades and exits axially, but in this invention the turbineblades 104 are impacted by an axial flow of the air stream 22. Theturbine blades 104 are shaped to act predominantly as an impulse turbineblade. The splitters 106, on the other hand, are shaped to functionpredominantly as a reaction turbine blade. They allow for maximum torqueor work out, while minimizing the drag torque or parasitic loss. Afurther description of the blade 104 and splitter 106 geometry isprovided below in connection with a discussion of the overall operationof the system 10.

One presently preferred embodiment of the turbine blades 104 of thisinvention is depicted in FIGS. 14-18 wherein a single blade 104 is shownin position on the turbine housing 72 for ease of illustration anddescription. In this embodiment, the diameter of the turbine 32 is 25inches (63.5 cm) which includes both the turbine housing 72 and theblades 104 and splitter 106, and the length “L” of the turbine 32 is 20inches (50.8 cm). Consequently, the length of each turbine blade 104 is20 inches (50.8 cm), and the length of each splitter 106 is about 10inches (25.4 cm). The height H1 of the blades 104 at the forward end 74of the turbine housing 72, measured between the blade root 108 and bladetip 110, is 8.4 inches (21.3 cm) and the height H2 at the aft end 76 is4.8 inches (12.2 cm). See FIG. 14. The angle “A” formed by the blade 74viewing it from the aft end 76 of the turbine housing 72 is about 76.5°,as shown in FIG. 17. Viewing the blade 104 from the forward end 74 ofthe blade housing 72, as depicted in FIG. 18, two angles “B” and “C” arepresented wherein angle B is about 6.5° and angle C is about 70.5°.Given these dimensions of the turbine housing 72 and blades 104, thereare preferably a total of five (5) blades 104 circumferentially spacedabout the turbine housing 104 and five (5) splitters 106 each located inbetween two adjacent blades 104. Further, there are preferably a totalof fourteen (14) inlet guide vanes 30 employed to direct the air stream22 to the blades 104 and splitters 106. However, it is contemplated thatother numbers of inlet guide vanes 30 could be employed so long as thetotal number is different than that of the blades 104 and splitters 106combined to ensure that only one inlet guide vane 30 aligns with one ofthe blades 104 or splitter 106 at any given time thus preventingacoustic resonance.

Referring now to FIGS. 2 and 19, the adjustable exhaust panels 36 ofthis invention are illustrated in more detail. In the presentlypreferred embodiment, a number of exhaust panels 36 are locateddownstream from the turbine 32 in a position to move between an openposition and a closed position with respect to one or more exhaustopenings 128 which extend substantially entirely about the outer surface15 of the pod housing 14. One end of each exhaust panel 36 is connectedby one or more hinges 130 to the pod housing 14. A pivot arm 132 isconnected at one end to each exhaust panel 36, and at the opposite endto an actuator ring 134. The actuator ring 134, in turn, is coupled tothe output of gear reducer 136 driven by a motor 138. The motor 138 andgear reducer 136 may be mounted within the pod housing 14 by a support140.

In response to operation of the motor 138 and gear reducer 136, theactuator ring 134 is rotated in a clockwise or counterclockwisedirection. In one direction of rotation of actuator ring 134, each pivotarm 132 is moved radially outwardly causing the exhaust panels 36 towhich it is connected to pivot outwardly from a “closed” position, i.e.a position in which the exhaust panels 36 rest against the outer surface15 of the pod housing 14 and close the exhaust opening(s) 128. It iscontemplated that the exhaust panels 36 may be configured to overlapwith one another when in the closed position to improve the seal madewith the exhaust opening(s) 128. In the presently preferred embodiment,the exhaust panels 36 may be moved to an open position, by rotation ofthe actuator ring 134 in the opposition direction, wherein an angle ofup to about 30° is formed relative to the outer surface 15 of the podhousing 14. For purposes of the present discussion, the term “openposition” refers to any amount of spacing between the exhaust panels 36and the outer surface 15 of the pod housing 14 up to an angle of about30°.

Having described the structural features of the system 10, its method ofoperation is now discussed. As an overview, system 10 is designed tomaximize free stream flow or the mass flow of an air stream through thepod interior 20 in order to enhance the torque produced by the hybridram air turbine 32, and, in turn, increase power generation. Bernoulli'stheorem states that the density of potential energy is proportional tothe pressure, whereas the density of kinetic energy is proportional tothe square of velocity. Applications where high pressures are available,such as conventional hydro-energy, generally employ turbines in whichblade area is maximized to increase torque. Most of the energy in suchsystems is obtain from potential energy or pressure differential, andefficiency may be increased by increasing blade area which, in turn,decreases velocity of the working fluid and increases pressure. On theother hand, low pressure exists in applications such as in pod 12mounted to the underside of an aircraft wing traveling at 220 or moreknots, at an altitude of 25,000, for example. In these applications, theenergy density is mainly kinetic energy and it is paramount to maximizethe velocity of the air stream, and avoid pressure buildup, in order toobtain as much torque from the turbine in the system as possible.

Several aspects of this invention contribute to the objective ofmaximizing the mass flow of the air stream 22 through the pod housing14. The submerged inlet 26 is effective to resist flow separation of theair stream 22 as it enters the pod interior 20. Flow separation resultsin flow recirculation which reduces the kinetic energy of the air stream22 in the course of passage downstream from the submerged inlet 26 tothe guide vanes 30 and turbine 32.

Maintenance of the kinetic energy of the air stream 22 as it movesthrough the pod 12 is also enhanced by creating a pressure drop in theaft portion of the pod interior 20. This pressure drop is induced byboth the shape of the turbine housing 72 and the presence of theadjustable exhaust ducts 36. As discussed above, the turbine housing 72decreases in cross section from its forward end 74 to the aft end 76.The spacing or gap between the outer surface 78 of the turbine housing72 and the pod housing 14 therefore increases moving in the aftdirection causing a pressure drop within the pod interior 20. Thispressure drop is enhanced or augmented by moving the exhaust ducts 36from a closed position to an open position as defined above. As thepressure within the pod interior 20 decreases, the velocity of airstream 22 is maintained or at least is not appreciably reduced.Additionally, the pressure drop or negative pressure created at the aftportion of the pod housing 14 tends to draw the air stream 22 into thepod interior 20.

Other features of this invention also contribute to maintaining or atleast not appreciably reducing the kinetic energy of air stream 22. Asdiscussed above, the splitters 106 on the turbine housing 72 are onlyabout 50% to 60% of the length of the blades 104, leaving spaces or openareas 124 in between the blades 104. These open areas 124 resist chokingor blockage of the air flow 22 as it passes through the turbine 32 whichwould otherwise reduce kinetic energy. Additionally, the forward end 112of each blade 104 is shaped to reduce drag in the direction of rotationof the turbine 32, and the aft end 114 thereof may be formed with anotch 142, depicted in phantom lines in FIG. 11, to reduce flowseparation and, thus, rotational drag.

Another overall objective of the system 10 of this invention is toextract as much work as possible out of the kinetic energy of air stream22 so that the torque produced by the turbine 32 is maximized. Thisobjective is met by a combination of the louvers 42, inlet guide vanes30, turbine blades 104 and splitters 106. While the louvers 42 act as aclosure device to open and close the submerged inlet 26, they alsofunction to assist in directing the air stream 22 to the turbine 32 withas little flow separation as possible. An axial flow of the air stream22 across the blades 104 and splitters 106 is desirable, to the extentpossible.

Referring to FIG. 13, a schematic depiction is provided of the air flow22 in the course of its movement through the inlet guide vanes 30, theblades 104 and the splitters 106. Preferably, the cup-shaped surface 62of each inlet guide vane 30 forms and angle “D” with an axis 146, one ofwhich is shown in FIG. 13, and each of which is generally parallel tothe longitudinal axis of the pod housing 14. Preferably, the angle “D”is in the range of about 22° to 45°. The air stream 22 impacts thesurface 62 of each inlet guide vane 30 which deflects it into engagementwith the leading surface 146 of each turbine blade 104, as representedby arrow 144, and along the trailing surface 148 thereof as depicted byarrow 150. The air stream 22 is also deflected by the inlet guide vanes30 into engagement with the leading surface 152 of the splitters 106, asrepresented by arrow 154. Impact of the air stream 22 with the leadingsurface 146 of blades 104 and the leading surface 152 of the splitters106 causes the turbine 32 to rotate, and the magnitude of torquedeveloped is dependent on the kinetic energy of the air stream 22 withwhich such surfaces 146, 150 are impacted. Additionally, a positivepressure is created along the leading edge 146 of each blade 104 by theair flow represented by arrow 144, and a negative pressure exists alongthe trailing edge 148 due to the air flow represented by arrow 150. Thispressure differential contributes to the torque created by the turbine32, and, in turn, the power output of the system 10.

It is contemplated that some “tuning” of the system 10 may be desirableto optimize performance. In the embodiment described above withreference to a discussion of FIGS. 7-10, the system 10 may be providedwith a means to adjust the angle “D” with which each inlet guide vane 30is oriented with respect to an axis 146 as noted in FIG. 13. Suchadjustment would result in altering the point of impact of the airstream 22, represented by arrows 144, 150 and 154, with the blades 104and splitters 106, respectively, which may improve performance undercertain operating conditions.

While the invention has been described with reference to a preferredembodiment, it should be understood by those skilled in the art thatvarious changes may be made and equivalents substituted for elementsthereof without departing from the scope of the invention. In addition,many modifications may be made to adapt a particular situation ormaterial to the teachings of the invention without departing from theessential scope thereof.

For example, the particular dimensions given for the turbine 32 andblades 104 in connection with a discussion of FIGS. 14-18 are intendedfor purposes of illustration only. The size of these components, and theother elements of system 10, may be varied according to the applicationfor which the system 10 is intended.

Therefore, it is intended that the invention not be limited to theparticular embodiment disclosed as the best mode contemplated forcarrying out this invention, but that the invention will include allembodiments falling within the scope of the appended claims.

1. A turbine, comprising: a turbine housing having a first end, a secondend spaced from said first end and an outer surface, said turbinehousing having a cross section which decreases from said first end tosaid second end; a number of turbine blades mounted to said outersurface of said turbine housing and being circumferentially spaced fromone another, each of said turbine blades extending from said first endto said second end of said turbine housing; a number of splittersmounted to said outer surface of said turbine housing, each of saidsplitters being located in one of said spaces between adjacent turbineblades, each of said splitters extending from said first end of saidturbine housing to a termination point spaced from said second endthereof.
 2. The turbine of claim 1 in which each of said turbine bladesincludes a blade root located at said outer surface of said turbinehousing, a blade tip spaced radially outwardly from said blade root, aforward end located at said first end of said turbine housing and an aftend located at said second end of said turbine housing, said spacebetween said blade root and said blade tip defining a height dimension,said height dimension of said turbine blades increasing in a directionfrom said forward end toward said aft end thereof.
 3. The turbine ofclaim 2 in which said blade tips of said turbine blades collectivelyform a generally cylindrical shape.
 4. The turbine of claim 2 in whichsaid aft end of each of said turbine blades is formed with a notch. 5.The turbine of claim 2 in which each of said splitters includes asplitter root located at said outer periphery of said turbine housing, asplitter tip spaced radially outwardly from said blade root, a forwardend located at said first end of said turbine housing and an aft end,said space between said splitter root and said splitter tip defining aheight dimension, said height dimension of said splitters increasing ina direction from said forward end to said aft end thereof.
 6. Theturbine of claim 5 in which said splitter tips of said splitters andsaid blade tips of said turbine blades collectively form a generallycylindrical shape.
 7. The turbine of claim 1 in which each of saidturbine blades and said splitters has a length dimension measured in adirection between said first and second ends of said turbine housing,said length dimension of said splitters being about half of said lengthdimension of said turbine blades.
 8. The turbine of claim 1 in which anopen area is formed along said outer periphery of said turbine housingin between adjacent turbine blades at each termination point of one ofsaid splitters.
 9. The turbine of claim 1 in which said turbine housingis generally frusto-conical in shape.
 10. The turbine of claim 1 inwhich said turbine blades function predominantly as an impulse turbineblade.
 11. The turbine of claim 1 in which said splitters functionpredominantly as a reaction turbine blade.
 12. A ram air turbine for usewith a pod adapted to mount to the wing of an aircraft, the podincluding a pod housing having a forward end, an aft end and an outersurface collectively defining a pod interior, said ram air turbinecomprising: a turbine housing mounted within the pod interior in thepath of an air stream flowing in an axial direction through the podinterior, said turbine housing having a first end, a second end spacedin said axial direction from said first end and an outer surface, saidturbine housing having a cross section which decreases from said firstend to said second end; a number of turbine blades mounted to said outersurface of said turbine housing and being circumferentially spaced fromone another, each of said turbine blades extending from said first endto said second end of said turbine housing; a number of splittersmounted to said outer surface of said turbine housing, each of saidsplitters being located in one of said spaces between adjacent turbineblades, each of said splitters extending from said first end of saidturbine housing to a termination point spaced from said second endthereof.
 13. The ram air turbine of claim 12 in which each of saidturbine blades includes a blade root located at said outer surface ofsaid turbine housing, a blade tip spaced radially outwardly from saidblade root, a forward end located at said first end of said turbinehousing and an aft end located at said second end of said turbinehousing, said space between said blade root and said blade tip defininga height dimension, said height dimension of said turbine bladesincreasing in a direction from said forward end toward said aft endthereof.
 14. The ram air turbine of claim 13 in which said blade tips ofsaid turbine blades collectively form a generally cylindrical shape. 15.The ram air turbine of claim 13 in which said aft end of each of saidturbine blades is formed with a notch.
 16. The ram air turbine of claim13 in which each of said splitters includes a splitter root located atsaid outer periphery of said turbine housing, a splitter tip spacedradially outwardly from said blade root, a forward end located at saidfirst end of said turbine housing and an aft end, said space betweensaid splitter root and said splitter tip defining a height dimension,said height dimension of said splitters increasing in a direction fromsaid forward end to said aft end thereof.
 17. The ram air turbine ofclaim 16 in which said splitter tips of said splitters and said bladetips of said turbine blades collectively form a generally cylindricalshape.
 18. The ram air turbine of claim 12 in which each of said turbineblades and said splitters has a length dimension measured in a directionbetween said first and second ends of said turbine housing, said lengthdimension of said splitters being about half of said length dimension ofsaid turbine blades.
 19. The ram air turbine of claim 12 in which anopen area is formed along said outer periphery of said turbine housingin between adjacent turbine blades at each termination point of one ofsaid splitters.
 20. The ram air turbine of claim 12 in which saidturbine housing is generally frusto-conical in shape.
 21. The ram airturbine of claim 12 in which said turbine blades function predominantlyas an impulse turbine blade.
 22. The ram air turbine of claim 12 inwhich said splitters function predominantly as a reaction turbine blade.